Aeroplane.



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AEROPLANE.

APPLICATION- FILED JAN-16.19%.

Patented Apr. 15, 1919 V. V. CARSON.

v AEROPLANE.

I APPLICATION FILEIJ ]AN.16.I918. 1,300,927.

Patented Apr. 15, 1919.

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APPLICATION FILED JAN-16.1918.

Patented Apr. 15, 1919.

3 SHEETSSHEET 3- a rare as are. 1

VICTOR V. CARSON, F TACOMA, WASHINGTON.

AEROPLANE.

To all whom it may concern: p

Be it known that T, VIo'roR V. CARsoN, a citizen of the United States, residing at Tacoma, in the county of Pierce and btate of Washington, have invented certain new and useful Improvements in Aeroplanes, of

. which the following is a specification.

mon use and which, at the same time, will be stable when in flight.

' Another object which I have in view is the construction of an aeroplane which to a great extent will eliminate the use of brace rods pr wires which are objectionable through the likelihood of their being injured and due to the fact that they offer considerable air resistance.

With these and other objects in view, my invention will be more fully described, illustrated in the accompanying drawings and then specifically pointed out in the claims which form a part of this application.

In the drawings:

Figure 1 is a side elevation of my improved aeroplane,

Fig. 2 is a top plan view,

Fig. 3 is a front elevation,

Fig. lis a vertical sectional view taken on the line H of Fig. 1, a

Fig. 5 is an unassembled perspective view of one of the ribs of the supporting plane,

Fig. 6 is a detail side elevational view of the ailerons and their control wires.

My improved aeroplane has a fuselage 10 and chassis 11 of simple type and light construction, the fuselage being preferably built along a stream line design to ofier but little air resistance and resting at its forward end, whichis closed by a radiator 12, upona cross brace 13. Downwardly diverging struts 1 1 extend from the end portions of the cross brace and at their lower ends journal anv axle which carry alighting wheels 16. A main longitudinal frame member 12 extends rearwardly from beneath the fuselage, its

Specification of Letters Patent.

Patented Apr. 15, 1919.

Application filed January 16, 1918. Serial No. 212,119.

front end being connected to the central portion of the brace 13 and its rear end carrying 2. depending swiveled fork 18 supporting a rear alighting wheel 19. Front and rear masts 20am 21 extend vertically from this longitudinal frame member 17 the former being located immediately at the rear of the fuselage and the latter at the rear end of the frame member 17. These masts, as will be later apparent, form the main supports for the supporting plane of the machine. Cooperating with these masts and holding the supporting plane are the upwardly diverging extended ends 22 of the struts 14 and the upwardly diverging struts 23 which are secured at their lower ends to the frame member 17 approximately midway between the masts.

The supporting or sustaining plane 24r-carried by the masts and struts 22 and 23 is substantially rectangular in shape having a rounded'front end and a squared rear end and is arched transversely, the curvature increasing somewhat from the ends toward the center of the plane. This supporting plane consists of a frame including a pair of longr tudinally extending ribs 25 and a plurality of transverse bows 26. The bows 26, as best shown in Fig. 5, include the longitudinally curved or arched upper and lower sections 2? and 28 which are lashed or otherwise secured to each other at their ends. The upp section 27 intermediate its length and points at each side of its center is formed with depending abutments 29, wh lower section 28 is formed with corics ing upwardly projecting abutments 3 abutments of each section engaging free ends against the other section space the intermediate portions of the bow sec tions and provide a bow of truss formation. These lugs are staggered somewhat with respect to each other and the opposed faces of adjacent lugs .of the upper and lower sections are cut away, so that each pair of lugs prothe cross bows and the masts 20 and 21 are also secured to the cross bows. The upper ends of these masts project through the supporting plane 24 and are connected by a guy wire or brace rod 32. A pair of guy wires or brace rods 33 lead from the top of the forward mast to the front portion of the plane at either side of the center thereof, this front portion of the plane being strengthened and braced by a suitable U- shaped frame member 34 which defines the edge of the plane and which at its sides extends rearwardly, being connected to the first and second of the transverse bows. The rear end of the plane is braced by a transverse frame member 35 and guy wires or brace rods 36 lead from the upper end of the rear mast 21 to the ends of the frame member 35. Preferably the sides of the frame are braced by wires 37 located between the two thicknesses of the plane covering. Secured between the front and rear masts 20 and 21, the supporting plane 24 and the longitudinal frame member 17, is

a vertical stabilizing plane 38 which assists in holding the aeroplane against tilting movement and side drift. The upper and lower edges of this plane 38 are braced by wires 39 inclosed in the fabric forming the plane and the plane may be additionally braced by wires 40 extending diagonally from corner to corner thereof.

An elevating rudder 41 is hinged to the member of the frame having hinged cornice-- tion with the supporting plane, the ends of this cross arm projecting above and below the rudder, as clearly shown in Fig. 1. Control wires 45 and 46 lead from the upper and lower ends respectively of the cross I arm 44 and are passed, the first beneath and the latter above a brace guide 47 connecting the longitudinal ribs 25 at a point between the two rear bows. These wires are then led between the upper and lower layers of the fabric constitutingthe supporting plane, through the guide eyes formed by the central lugs of the bows and down the forward mast into the fuselage, where they are connected to any suitable controlling lever or wheel, not shown, in such a manner that as one wire is pulled the other will be correspondingly slackened, so that the rudder may be pulled up or down, at will.

A cross piece secured intermediate its 'length to the chassis at the point of junction of the frame member 17 and the connecting ends of upwardly converging struts 48, the lower ends of which also journal the axle 15, provides arms 49 projecting to each side at the rear of the fuselage. These arms form supports for a pair .of ailerons 50 which are swingingly connected to the arms by hinge elements 51. Each of these ailerons is substantially rectangular in shape, having its rear end rounded somewhat and each includes the rectangular frame 52, the forward member of which is secured to the hinges, the frames being covered with fabric in the same manner as the frames of the supporting and stabilizing planes. At the inside of each of these ailerons and at the forward edges are cross arms 53 corresponding to the cross arm of the rudder. A control wire 54 leads. through the bottom of the fuselage and is connected to a wire 55 which in turn is connected to the upper end of.

one of the cross arms 53 and the wire 54 is connected to a mechanism which may be identical with that with which thewires of the elevating rudder coiiperate so that when either the wire 54 or the wire 57 is pulled, the other wire will be slackened. Pulling on either wire will therefore cause simultaneous and reverse tilting movement of the ailerons. Any suitable motor, not shown, serves to drive the propeller 59, the motor of course being disposed in the for-' ward end of the fuselage andthe pro peller in advance thereof.

Swingingly supported by the rear mast 21 is a vertical rudder 60 for controllingthe lateral direction of the aeroplane. This rudder, at its lower end,'is provided with a cross arm 61 corresponding to the cross arm 44, and control wires 62 lead from the ends of the cross arm through suitable guides carried by the frame member 17 and into the fuselage where they are connected to a further controlling mechanism correspond ing to that of the elevating rudder and the ailerons. This rudden 60 includes a frame .corresponding to the frame of the elevating zontal when the aeroplane is at rest upon the ground, its forward end being at a considerable elevation above its rear end. Be-

'cause of this, as soon as the propeller is put in motion, the plane will rise and this rising of the plane will be accelerated by a proper tilting of the elevating rudder, which will also serve to direct changes in elevation during flight, while the steering rudder will serve to control the lateral course of the aeroplane. In case of tilting to one side or the other due to air currents or pockets, the ailerons or balancing planes will be tilted in the usual manner to overcome the trouble.

Having thus described the invention, what is claimed as new is:

1. An aeroplane comprising a chassis, a fuselage mounted on the forward end of the chassis, a vertically disposed longitudinally extending stabilizing plane supported on the chassis and extending from the rear end of the fuselage to the rear end of the chassis, and a longitudinally extending sustaining plane supported from the chassisdirectly over the fuselage and the stabilizing plane and extending forwardly beyond the front end of the fuselage.

' 2. An aeroplane comprising a chassis, a longitudinal frame member supported by the chassis, a fuselage secured on the forward portion of said frame member, diverging struts rising from the sides of the fuselage and from the frame member in rear of the fuselage, masts-rising from the frame member at the rear end of the fuselage and the rear end of the frame member, a vertically disposed stabilizing plane secured to said masts and the frame member, longitudinal ribs carried by the upper ends of the struts, transverse bows carried by said ribs, and a sustaining plane supported by said ribs and bows.

3. An aeroplane comprising a chassis, a fuselage mounted on the front end of the chassis, a vertically disposed longitudinally extending stabilizing plane secured on the chassis and extending from the rear end of the fuselage t0 the rear end of the chassis, a longitudinally extending sustaining plane supported from the chassis above the fuselage and the stabilizing plane and extending forwardly beyond the fuselage, a cross bar secured on the chassis at the junction of the rear end of the fuselage and the lower corner of the front end of the stabilizing plane, ailerons mounted on said cross bar at the sides of said plane, and means Within the fuselage for controlling the ailerons.

4. In an aeroplane construction, a chassis a fuselage mounted at the forward end of the chassis, a longitudinally extending supporting plane disposed above the chassis and fuselage and inclining upwardly from its rear to its forward end, an elevating rudder mounted upon the rear end of the supporting plane, a vertically disposed longitudinally extending stabilizing plane located below the supporting plane and at the rear of the fuselage, a laterally swinging rudder mounted at the rear end of the stabilizing plane, ailerons mounted one at either side of the forward end of the stabilizing plane, and means for simultaneously and reversely tilting the ailerons.

In testimony whereof I affix my signature.

VICTOR v. CARSON. 1.8. 

